Turbojet fuel



Patented Sept. 2, 9.52

. V gen, Jr., Roselle. Park,"N,J s

. .forsito Standard Oil Deveiopment com corporatio gn l 1a I NfiDrawing.

part'dii'World War llhasbeenvery rapid. 'LThe advanceshave been spurred on by the potential high speed performance possibilities of "jet-propelled craft compared with the propelleridi'iven type which attaintheirbest efiicienc-ies atllow'er air speeds. V r 1 Early aviation =.turbo+jet=' engines and most or f those presently in -useweredesigned tooperatewith a low aromatic, akerosene-tyraav fuelialmost identical with domestic kerosene. Combustor designs, which were developed originally bv a cut-and-try method,ihave been adiusted to this fuel by subsequent designs until performance and maintenance for sea, level and limited altitude operation are approaching satisfactory limits.

With the increased use of jet engines has arisen the logical question of fuel supply for probable ,exnanding commercial requirements and for possible more immediate military emergencies. These sup ly requirements have necessitated institution of the present broad specifications for a 5-7 lb. RVP, 600 FEP fuel containing higher percentages of aromatics, olefins, and sulfur. Such liberalizing in petroleum fuel specifications will result in better than a three-fold increase in supplies with less problems in feed stock selection and segregation for the fuel supplier.

The changing of fuel specifications has imposed problems of engine deposition in present, engine combustors.

It has now been found that the amount of carbon deposited on vital engine parts can be greatly reduced by adding 0.1 to 5% by weight of a hydroperoxide to a turbo-jet fuel high in aromatic hydrocarbons.

The following examples illustrate the advantages to be secured by the practice of the present invention:

ilpplicafio phlovember 26.1949, Serial No. 129,596

2 Claims. (01. 44 57) .flwampldi'i j A high aromatic "jet fuel having the following :inspBption GTaiVity-. Renrvaponpr ap 'ilfdas'hipointl'lagcc i150 ASTM distillati'on,Fa

-I. B.;P.-..... a.,.; ..e... .a .a; "347 10% l a. 378 0% V 8 V 90%-..' 3133 'F. B. P. 425 Freezing point fF. a .-l0 .Corrosion test qsulfur, sweight percent f 11.026 iAromatics, volume percent ,ATSM

ES- .g... 919 .Brommemumber cg/g. Wanna-reassess; -0 i3 Viscosity, centistokes:

At --40 F At F ASTM gum, mg./100 m1 18.9 ACC. Army Gum Test, mg/100 ml.:

7 hours 16 hours Net heating value, B. t. u./lb. 17,775

was burned in the General Electric 1-40 single combustor engine with and without the addition of 2 weight percent cumene hydroperoide and the following data were obtained:

I 41 57 5s] Jet Fuel Cume ne Hydroperoxide 3 The above data show that the quantity of carbon was reduced 62 A check run showed about the same percentage of carbon reduction.

Example II A test similar to that of Example I was carried out using a non-aromatic fuel having the following inspection:

4 The above examples show that the addition of cumene hydroperoxide is effective in reducing the carbon deposition tendency of a jet fuel only when it contains a very'large amount of arc- 5 matics.

The nature of the present invention having thus been described, what is claimed as new and useful and desired to be secured by Letters Patent is Gravity, 10 1. A fuel for use in turbo-jets in which the Reid vapor pressure, p. s.i oxygen required for combustion of the fuel is Flash P 1 00-), supplied by air, said fuel consisting essentially AS M Di t w of a liquid hydrocarbon composition containing 115 at least 50% by volume of aromatic hydrocar- 154 v bons and 0.1 to 5% by volume of cumene hydro- 391 peroxide. 90% 510 "2. Composition as defined by claim 1 wherein P 5' the amount of cumene hydroperoxide present is Freezin poi t, -76 about 2% by volume. Corrosion t t P s KENNETH MORRIS Sulfur. w t p t RAYMOND A VAN SWERINGEN JR Aromatics, volume percent by ASTM V REFERENCES CITED Bromine number, cg./g 5.87 I

The following references are of record in the Viscosity, centistokes. m f t t. At 40o F 392 e 0 15 p en At F UNITED STATES PATENTS ASTM Gum, mg./100 m1.: a

7 hrs 1&0 Number Name Date 16 hrs 215 30 1,766,501 Buerk June 24, 1930 I b 1 51 2, 03,7 2 Vaughan 913 8,1 July 9, 196 N? value B u A. 2,472,152 Farkas June '1. 1949 When this fuel was burned with and without 2,534,309 shemeld 191 1950 the addition of 2 weight percent of cumene hydroperoxida'it'was found that the cumene hy- FOREIGN PATENTS "droperoiiide" had substantially no efiect on the Number Country Date carbon formation as shown in the following table: 476,227 Great Britain June 4, 1937 I n Com- Oom- Air Rate Air/Fuel Length E 12? hi2? Carbon Deposit'g' B N0 Fuel Used lb./sec. Ratio -E3 Air Air sumed, Temp., Press, g.

F. p.s.i. Dome Liner Total 1 Non-aromatic 2.fl 4.25 300 48 278 2.9 8.5 11.4 2 -410 2.0 50 4. 25 300 48 218 2.5 7.5 10.0 a do 2.0 50 4.25 300 48 278 1.5 7.0 as 4 +2% Cumene Hydro 2.0 50 4.25 s00 48 '27s at 11.0 14.4 v peroxide. 

1. A FUEL FOR USE IN TURBO-JECTS IN WHICH THE OXYGEN REQUIRED FOR COMBUSTION OF THE FUEL IS SUPPLIED BY AIR, SAID FUEL CONSISTING ESSENTIALLY OF A LIQUIID HYDROCARBON COMPOSITION CONTAINIINNG AT LEAST 50% BY VOLUME OF AROMATIC HYDROCARBONS AND 0.1 TO 5% BY VOLUME OF CUMENE HYDROPEROXIDE. 